EP2227629B1 - Dispositif de chambre de combustion - Google Patents

Dispositif de chambre de combustion Download PDF

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Publication number
EP2227629B1
EP2227629B1 EP08863553A EP08863553A EP2227629B1 EP 2227629 B1 EP2227629 B1 EP 2227629B1 EP 08863553 A EP08863553 A EP 08863553A EP 08863553 A EP08863553 A EP 08863553A EP 2227629 B1 EP2227629 B1 EP 2227629B1
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EP
European Patent Office
Prior art keywords
fluid
combustion chamber
accordance
prechamber
section
Prior art date
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German (de)
English (en)
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EP2227629A2 (fr
Inventor
Johannes Lux
Dmitry Suslov
Oskar Haidn
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Deutsches Zentrum fuer Luft und Raumfahrt eV
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Deutsches Zentrum fuer Luft und Raumfahrt eV
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/52—Injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F05D2240/36—Fuel vaporizer

Definitions

  • the present invention relates to a combustion chamber device comprising a combustion chamber, a first injector device for introducing a first fluid into the combustion chamber and a second injector device for introducing a second fluid into the combustion chamber.
  • an injection head for supplying combustion in a combustion chamber causing media is known.
  • the injection head is made up of at least two segments that are coaxial with each other in an axis.
  • the at least two segments have at least one distribution channel with an associated elongate outlet region for a flow of a first medium and at least one distribution channel with an associated elongate outlet region for a second medium flow limiting wall regions and the elongated outlet region for the first medium and the elongated outlet region for the second medium are coaxial with each other and at least in an angular range of 360 ° around the axis formed circumferentially.
  • a near-combustion generator is known, the first liquid fuel supply devices and second liquid fuel supply devices, a porous body through which a flow rate of the first liquid fuel is injected into a combustion chamber bounded by one of the surfaces of the porous piece, and devices for injecting an amount of the second fuel in the porous part or in close proximity to the surface of the porous part defining the combustion chamber.
  • a mixture of first and second fuel is formed in the porous part or in close proximity to the said area of the porous part defining the combustion chamber.
  • the porous body is annular and said means for injecting a quantity of second fuel are shaped so that the injection of the second fuel is substantially radial.
  • At least one porous main body calibration equipment which includes calibration ports for ensuring modulation of the injection rate of the first liquid fuel into the combustion chamber, wherein at least one of the parameters formed by the dimension of the calibration ports, namely the distance between the adjacent calibration ports and the number of calibration ports per Unit surface, is variable depending on the axial position of the calibration holes in the calibration equipment.
  • a combustion chamber for gas turbine engines which is equipped with means for supplying and processing of the fuel.
  • the upstream flame tube wall of the combustion chamber of one or more flow-permeable elements is interspersed with these upstream assigned fuel injectors.
  • a combustion chamber which comprises an arrangement of porous injector elements.
  • an injector system for a rocket motor which has a space with at least one porous element.
  • a change in the mass flows of the first fluid and the second fluid is usually accompanied by a corresponding change in the mass flows of the first fluid and the second fluid.
  • the injector devices For the most efficient possible reaction of the first fluid and the second fluid, they must be introduced into the combustion chamber with the aid of the injector devices in such a way that they are present in finely distributed, homogeneous form in order to allow good mixing and combustion.
  • the present invention the object of the invention to provide a combustion chamber device of the type mentioned, with which an efficient combustion is ensured even with a change in the mass flows of the first fluid and the second fluid.
  • the first injector device comprises at least a first porous element, which is traversed by the first fluid and which limits at least a portion of the combustion chamber
  • the second injector device comprises at least one second porous element , which can be traversed by the second fluid
  • a fluid guide device is provided with at least one fluid conduit for guiding the second fluid between the second element and the combustion chamber and that the at least one fluid conduit passes through the first element.
  • the fluids can be introduced in finely divided form into the combustion chamber. This allows a homogeneous distribution and mixing of fluids, ensuring efficient combustion. In a liquid fluid is also supported by the fine distribution of the fluid in the combustion chamber evaporation of this fluid, so the transition from the liquid to the gaseous phase.
  • porous elements has the further advantage that the pressure loss applied via these porous elements is very low in comparison with injector devices which comprise what are called coaxial injectors. This makes it possible to reduce the performance of the fluid supply systems which supply fluid to the injector devices.
  • the porous elements have the further advantage that they allow a particularly good decoupling between the combustion chamber and an upstream fluid supply system.
  • the porous elements act as damping elements against pressure oscillations or shocks. Such damping is particularly advantageous when the combustion chamber device is operated in a wide power range and thus pressure oscillations in a wide frequency range and possibly also at a resonant frequency of the injection system can occur. This leads to an increased mechanical load of the injection system and to increased acoustic emissions of the combustion chamber device. These negative effects can at least be mitigated with the aid of the porous elements of the injector devices.
  • porous elements are particularly well cooled by the flow with one of the fluids. This makes it possible to shift the combustion zones of the combustion chamber closer toward at least one of the injector devices. This makes it possible to downsize the combustion chamber. As a result, space and weight advantages can be achieved.
  • the porous elements also make it possible to shield areas outside the combustion chamber from the combustion chamber. In particular, flashback or flame quenching can be prevented.
  • the first element limits at least a part of the combustion chamber. In this way, a treated by means of the first element fluid can be introduced directly into the combustion chamber.
  • the fluid guiding device comprises at least one fluid line. It is particularly preferred if a plurality, in particular a plurality of fluid lines is provided. With the aid of the at least one fluid line, the second fluid prepared by means of the second element can be introduced into the combustion chamber. With a plurality of fluid lines, it is possible to provide a plurality of fluid introduction areas, whereby a particularly good distribution of the second fluid is ensured in the combustion chamber.
  • the at least one fluid line passes through the first element. This makes it possible to pass the second fluid through the first element with the aid of the fluid line, without the second fluid already coming into contact with the first fluid outside the combustion chamber.
  • the first injector device comprises a first prechamber for storing the first fluid.
  • a space can be created in which pressure vibrations of the first fluid can be reduced.
  • the first element delimits at least a part of the first prechamber. This makes it possible to damp vibrations of the first fluid within the first pre-chamber and to supply this fluid directly to the first element.
  • the first element is arranged between the first prechamber and the combustion chamber. As a result, a particularly simple first injector device can be created.
  • the second injector device comprises a second prechamber for storing the second fluid. This allows vibration damping of the second fluid.
  • the second element defines at least a portion of the second antechamber.
  • a second fluid damped by means of the second pre-chamber second fluid can be supplied directly to the second element.
  • the second element is arranged between a first prechamber for storing the first fluid and a second prechamber for storing the second fluid. This enables a compact construction of the first injector device and the second injector device.
  • the at least one fluid line has a line cross-section of at most approximately 10 mm 2 .
  • This has the advantage that a fluid treated with the aid of the second element can be supplied to the combustion chamber at a high flow rate.
  • the at least one fluid line may, for example, have a circular flow cross-section, the diameter of which may be in particular between 0.5 mm and 3 mm.
  • At least a portion of the at least one fluid line is arranged within a first prechamber for storing the first fluid. This allows the construction of a particularly compact first injector device and second injector device.
  • the fluid guiding device comprises a fluid guiding element for guiding the second fluid between a fluid outlet surface of the second element and a fluid inlet surface of the at least one fluid line. This makes it possible to provide a large fluid outlet area compared to the fluid inlet surface of the at least one fluid line. This allows a correspondingly large-scale treatment of the second fluid.
  • the fluid guide element has a fluid guide surface arranged adjacently to the fluid outlet surface of the second element. This allows a particularly simple guidance of the fluid after exiting the fluid outlet surface and before entering the fluid line.
  • At least a portion of the fluid outlet surface of the second element and at least a portion of the fluid guide surface of the fluid guide element abut each other. In the region of the adjoining sections can thus be prevented in a simple manner, an exit of the second fluid from the second element.
  • At least one spacer element is provided for spacing at least a portion of the fluid outlet surface of the second element and at least a portion of the fluid guiding surface of the fluid guiding element.
  • a spacer allows a simple determination of the distance between the second element and the fluid guide element and thus a dimensioning of a damping fluid space acting.
  • the at least one spacer element is integrally formed with the fluid guide element. This simplifies the manufacture and assembly of the combustion chamber device.
  • a further preferred embodiment of the invention provides that at least a portion of the fluid outlet surface of the second element and the fluid inlet surface of the at least one fluid line abut each other. This allows an immediate transfer of the second fluid from the second element into the fluid line.
  • At least a portion of the fluid outlet surface of the second element and the fluid inlet surface of the at least one fluid line are spaced from each other. In this way, a reliable coupling of the second fluid into the fluid line is ensured even when the fluid line has a very small fluid inlet area and when the second element has relatively coarse pore boundaries.
  • first element and the second element are made in one piece with each other. This results in a particularly simple construction of the combustion chamber device.
  • the fluid guiding device, the first element and the second element are made in one piece with each other.
  • At least one of the elements is plate-shaped.
  • the thickness of a plate-shaped element defines the flow path available through the element for the first or the second fluid.
  • the extension of the plate in a direction perpendicular to the plate thickness defines the size of the fluid entry surface for a fluid to be treated by the element and the size of the fluid exit surface for a treated fluid.
  • a particularly advantageous embodiment of the invention provides that the first element and the second element are different porous. As a result, an optimal treatment of different in terms of their composition and / or their phase state first and second fluids is possible.
  • At least one of the elements is made of a metallic material.
  • a metallic material can be made of sintered metal or metal foam, for example sintered bronze.
  • Metallic materials have the advantage of high thermal conductivity.
  • At least one of the elements is made of a ceramic material and thus particularly insensitive to high temperatures.
  • first element and the second element can be flowed through in directions at least approximately parallel to each other.
  • first fluid and the second fluid can be conducted into the combustion chamber in the same directions without having to divert at least one of the fluids for this purpose.
  • the combustion chamber has a central combustion chamber axis.
  • the combustion chamber is rotationally symmetrical to the central combustion chamber axis, for example cylindrical.
  • the first element and the second element along the combustion chamber axis are arranged one behind the other. This enables a preparation of the first fluid and the second fluid and a supply into the combustion chamber in mutually parallel directions.
  • At least one of the elements has different element thicknesses in directions parallel to the combustion chamber axis.
  • the flow resistance of an element can be influenced locally, in particular in order to influence the introduction of the treated fluid into the combustion chamber.
  • At least one of the elements has a symmetrical element thickness distribution with respect to the combustion chamber axis. In this way, a symmetrical introduction to the combustion chamber axis of a treated fluid is ensured in the combustion chamber inside.
  • At least one of the elements has a center section relative to the combustion chamber axis and a section decentralized relative to the combustion chamber axis, wherein an element thickness of the decentralized section is higher than an element thickness of the central section.
  • an introduction of the fluid into the combustion chamber in a central region of the combustion chamber can be increased and reduced in a decentralized region of the combustion chamber.
  • a reduced mixing ratio can be achieved, whereby the heat load of the combustion chamber wall decreases.
  • a further embodiment of the invention provides that the combustion chamber device has at least one combustion chamber housing which at least one of the elements is releasably fastened or fastened. This allows replacement of the at least one element, for example for maintenance purposes, or to optimize the combustor device for the use of a particular fluid.
  • the first fluid is a fuel, in particular hydrogen, methane or ethanol.
  • the first fluid is present in a gaseous or supercritical state on entry into the first element.
  • a fuel is in the form of hydrogen in a supercritical state of pressure and temperature.
  • a fuel in the form of methane is preferably present in a supercritical state, at least in terms of pressure.
  • ethanol When using ethanol as a fuel, it may also be in a liquid state.
  • the second fluid is an oxidizer, for example oxygen.
  • the second fluid is in a liquid or supercritical state upon entering the second element.
  • an oxidant in the form of oxygen is in a supercritical state of pressure ("compressed liquid” or "subcooled liquid”).
  • the invention further relates to an engine with a combustion chamber device described above, in particular a rocket engine.
  • a rocket engine can be operated in particular with cryogenic fluids.
  • the invention further relates to a heating device with a combustion chamber device described above, in particular a boiler.
  • the combustion chamber device according to the invention can also be used in aeronautical drives, in gas turbines, in process engineering, in the chemical industry and are used in internal combustion engines, especially of motor vehicles.
  • FIG. 1 One embodiment of a rocket designated 10 is shown in FIG FIG. 1 shown.
  • the rocket 10 has a main body 12 with which a payload unit 14 can be carried.
  • the rocket 10 further includes two solids boosters 16.
  • the main body 12 has a first tank 18 for a first fluid.
  • the first fluid is, for example, a fuel, in particular liquid hydrogen.
  • the main body 12 further includes a second tank 20 for a second fluid.
  • the second fluid is in particular an oxidizer, for example liquid oxygen (LOX).
  • LOX liquid oxygen
  • the main body 12 of the rocket 10 has an engine 22, which includes a combustion chamber device 24 ( Fig. 2 ).
  • the combustor device 24 includes a combustor 26 in which the first fluid and the second fluid react with each other to produce a thrust to propel the missile 10.
  • the combustion chamber 26 is bounded by means of a particular cylindrical combustion chamber housing 28. This extends along a central combustion chamber axis 30.
  • the combustion chamber device 24 has a first injector device 32 for introducing the first fluid into the combustion chamber 26.
  • the first injector device 32 comprises a porous first element 34, which is preferably plate-shaped.
  • the first element 34 extends in particular transversely to the combustion chamber axis 30 and limits the combustion chamber 26 together with the combustion chamber housing 28.
  • the first injector device 32 comprises a first prechamber 36, which is fluidically connected to the first tank 18 of the rocket 10.
  • the combustion chamber device 24 further comprises a second injector device 38 with a second porous element 40.
  • the element 40 is in particular plate-shaped.
  • the second element 40 adjoins a second prechamber 42, which is fluidly connected to the second tank 20 of the rocket 10.
  • the first element 34 and the second element 40 are arranged one behind the other along the combustion chamber axis 30.
  • the first element 34 is disposed between the combustion chamber 26 and the first prechamber 36.
  • the second element 40 is arranged between the first prechamber 36 and the second prechamber 42.
  • the first element 34 has a fluid inlet surface 44 applied to the combustion chamber 36 and a fluid outlet surface 46 facing the combustion chamber 36.
  • a first fluid contained in the first pre-chamber 36 enters the first element 34 via the fluid inlet surface 44, flows through it, exits again at the fluid outlet surface 46 and enters the combustion chamber 26 in finely distributed form.
  • the second element 40 has a fluid inlet surface 48 facing away from the combustion chamber 26 and a fluid outlet surface 50 facing the combustion chamber 26.
  • a second fluid contained in the second prechamber 38 enters the second element 40 via the fluid inlet surface 48, flows through it and reaches the fluid outlet surface 50.
  • the combustion chamber device 24 For guiding the second fluid between the fluid outlet surface 50 of the second element 40 and the combustion chamber 26, the combustion chamber device 24 comprises a fluid guiding device 52.
  • the fluid guiding device 52 comprises a fluid guiding element 54 which is in particular plate-shaped is trained.
  • the fluid guide element 54 is arranged between the first pre-chamber 36 and the second element 40.
  • the fluid guiding device 52 furthermore comprises a plurality of fluid lines 56, which establish a fluid-effective connection between the fluid outlet surface 50 of the second element 40 and the combustion chamber 26.
  • the fluid lines 56 extend in particular parallel to the combustion chamber axis 30.
  • at least one fluid line extends obliquely to the combustion chamber axis 30;
  • a second fluid introduced into the combustion chamber 26 with the aid of the fluid lines 56 can be supplied to different focal points.
  • the fluid lines 56 have a fluid inlet surface 58 facing the fluid outlet surface 50 of the second element 40 and a fluid outlet surface 60, which is preferably arranged at the height of the fluid outlet surface 46 of the first element 34 or within the combustion chamber 26.
  • the fluid lines 56 are in particular cylindrical and have a diameter of preferably between about 0.5 mm and about 3 mm.
  • the fluid guide element 54 has a fluid guide surface 62, which is arranged adjacent to the fluid outlet surface 50 of the second element 40.
  • the fluid guide surface 62 prevents penetration of the second fluid into the first pre-chamber 36.
  • the fluid guide element 54 has a multiplicity of perforations 64, which each serve to receive a conduit wall 66 of a fluid line 56.
  • the first element 34 has corresponding apertures 68 for the conduit wall 66 of a fluid conduit 56.
  • a second fluid contained in the second prechamber 42 is supplied to the combustion chamber 26 by means of the fluid guiding device 52, without the second fluid already being at the level of the first prechamber 36 and / or at the height of the first prechamber 36 first element 34 in contact with the first fluid device. Because the fluid guiding device 52 has a plurality of fluid lines 56, this can be introduced into the combustion chamber 26 in finely divided form with the aid of the second element 40.
  • At least a portion of the fluid outlet surface 50 of the second element 40 rests against at least a portion of the fluid guiding surface 62 of the fluid guiding element 54 (cf. Fig. 3 ).
  • At least a portion of the fluid exit surface 50 of the second element is spaced from the fluid guide surface 62 of the fluid guide element 54 (see FIG. Fig. 4 ).
  • at least one spacer element 70 is provided, which in particular is formed integrally with the fluid guide element 54.
  • the spacing of the surfaces 50 and 62 results in a fluid space 72 which has a fluid-dynamic damping effect. A particularly good damping effect is achieved if the fluid inlet surface 58 is also spaced from the fluid outlet surface 50 (cf. 4 and 5 ).
  • a spacing of the fluid outlet surface 50 from the fluid line 56 can be achieved by means of the spacer elements 70 (described above). Fig. 4 ) and / or in that the fluid guiding element 54 is provided with a recess 74 ( Fig. 5 ).
  • FIGS. 6 and 7 Embodiments of fluid routing elements 54 are shown as viewed in accordance with FIG FIG. 4 Direction VI. In the FIGS. 6 and 7 the second elements 40 and the fluid lines 56 are not shown for reasons of clarity.
  • the spacer elements 70 may, for example, have a circular course ( Fig. 6 ). In particular, a plurality of spacer elements 70 may be provided which run concentrically to the combustion chamber axis 30. Alternatively, the spacers 70 may also in a with respect to the combustion chamber axis 30 extend radial direction (see. Fig. 7 ). For example, four spacer elements 70 may be provided, which in each case enclose a right angle in pairs.
  • At least one of the porous elements 34, 40 may have different element thicknesses.
  • An element thickness of an element 34, 40 is defined by the distance between a fluid inlet surface and a fluid outlet surface of an element.
  • a second element 40 may have a central portion 76 in which the element 40 has a comparatively low element thickness 78 ( Fig. 8 ).
  • the element 40 may have a decentralized portion 80 which has a higher element thickness 82 compared to the element thickness 78.
  • portions of a porous member 34, 40 having a lower element thickness are disposed in the region of the combustor axis 30, and remote portions having a higher element thickness are spaced from the combustor axis 30 and preferably disposed adjacent to the combustor housing 28.
  • the distribution of the element thicknesses can be symmetrical with regard to the combustion chamber axis 30 and / or asymmetrically. It is preferred if the porous elements have a continuous element thickness profile 84 (FIG. Fig. 8 ) or 86 ( Fig. 9 ) exhibit.
  • At least one of the porous elements 34, 40 has a dome-shaped fluid inlet surface and / or fluid outlet surface and / or a dome-shaped fluid guide element 54 is provided.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (15)

  1. Dispositif de chambre de combustion (24), comprenant une chambre de combustion (26), un premier dispositif injecteur (32) pour l'introduction d'un premier fluide dans la chambre de combustion (26) et un second dispositif injecteur (38) pour l'introduction d'un second fluide dans la chambre de combustion (26), caractérisé en ce que le premier dispositif injecteur (32) comporte au moins un premier élément poreux (34) qui peut être traversé par le premier fluide et qui délimite au moins une partie de la chambre de combustion (26), en ce que le second dispositif injecteur (38) comporte au moins un second élément poreux (40) qui peut être traversé par le second fluide, en ce qu'un dispositif de guidage de fluide (52) avec au moins une conduite de fluide (56) est prévu pour le guidage du second fluide entre le second élément (40) et la chambre de combustion (26) et en ce qu'au moins une conduite de fluide (56) traverse le premier élément (34).
  2. Dispositif de chambre de combustion (24) selon la revendication 1, caractérisé en ce que le premier dispositif injecteur (32) comporte une première préchambre (36) servant de réservoir au premier fluide.
  3. Dispositif de chambre de combustion (24) selon la revendication 2, caractérisé en ce que le premier élément (34) délimite au moins une partie de la première préchambre (36), et en particulier en ce que le premier élément (34) est disposé entre la première préchambre (36) et la chambre de combustion (26).
  4. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que le second dispositif injecteur (38) comporte une seconde préchambre (42) servant de réservoir au second fluide, et en particulier en ce que le second élément (40) délimite au moins une partie de la seconde préchambre (42).
  5. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que le second élément (40) est disposé entre une première préchambre (36) servant de réservoir au premier fluide et une seconde préchambre (42) servant de réservoir au second fluide.
  6. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins une section d'au moins une conduite de fluide (56) est disposée dans une première préchambre (36) servant de réservoir au premier fluide.
  7. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que le dispositif de guidage de fluide (52) comporte un élément de guidage de fluide (54) pour le guidage du second fluide entre une surface de sortie de fluide (50) du second élément (40) et une surface d'entrée de fluide (58) d'au moins une conduite de fluide (56), et en particulier en ce que l'élément de guidage de fluide (54) présente une surface de guidage de fluide (62) disposée de manière contiguë à la surface de sortie de fluide (50) du second élément (40), et en particulier en ce qu'au moins une section de la surface de sortie de fluide (50) du second élément (40) et au moins une section de la surface de guidage de fluide (62) de l'élément de guidage de fluide (54) reposent l'une sur l'autre, et en particulier en ce qu'au moins une section de la surface de sortie de fluide (50) du second élément (40) et au moins une section de la surface de guidage de fluide (62) de l'élément de guidage de fluide (54) sont espacées l'une de l'autre, et en particulier caractérisé par au moins un élément d'écartement (70) destiné à écarter au moins une section de la surface de sortie de fluide (50) du second élément (40) et au moins une section de la surface de guidage de fluide (62) de l'élément de guidage de fluide (54), et en particulier en ce qu'au moins un élément d'écartement (70) est réalisé d'un seul tenant avec l'élément de guidage de fluide (54), et en particulier en ce qu'au moins une section de la surface de sortie de fluide (50) du second élément (40) et la surface d'entrée de fluide (58) d'au moins une conduite de fluide (56) reposent l'une sur l'autre, et en particulier en ce qu'au moins une section de la surface de sortie de fluide (50) du second élément (40) et la surface d'entrée de fluide (58) d'au moins une conduite de fluide (56) sont espacées l'une de l'autre.
  8. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que le dispositif de guidage de fluide (52) et le second élément (40) sont fabriqués d'un seul tenant et/ou en ce que le premier élément (34) et le second élément (40) sont fabriqués d'un seul tenant.
  9. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que le premier élément (34) et le second élément (40) présentent une porosité différente.
  10. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins l'un des éléments (34, 40) est fabriqué en un matériau métallique.
  11. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins l'un des éléments (34, 40) est fabriqué en un matériau céramique.
  12. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que le premier élément (34) et le second élément (40) peuvent être traversés dans des sens au moins approximativement parallèles.
  13. Dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes, caractérisé en ce que la chambre de combustion (26) présente un axe de chambre de combustion (30) central, et en particulier en ce que le premier élément (34) et le second élément (40) sont disposés l'un derrière l'autre vu le long de l'axe de chambre de combustion (30), et en particulier en ce qu'au moins l'un des éléments (34, 40) présente différentes épaisseurs d'élément (82) dans des sens parallèles à l'axe de chambre de combustion (30), et en particulier en ce qu'au moins l'un des éléments (34, 40) présente une répartition d'épaisseur d'élément symétrique à l'axe de chambre de combustion (30), et en particulier en ce qu'au moins l'un des éléments (34, 40) présente une section centrale par rapport à l'axe de chambre de combustion (30) et une section (80) décentralisée par rapport à l'axe de chambre de combustion (30), sachant qu'une épaisseur d'élément (82) de la section décentralisée (80) est supérieure à une épaisseur d'élément (78) de la section centrale (76).
  14. Turbine (22) avec un dispositif de chambre de combustion (24) selon l'une quelconque des revendications précédentes.
  15. Dispositif de chauffage avec un dispositif de chambre de combustion (24) selon l'une quelconque des revendications 1 à 13.
EP08863553A 2007-12-21 2008-12-15 Dispositif de chambre de combustion Active EP2227629B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007063539A DE102007063539A1 (de) 2007-12-21 2007-12-21 Brennkammervorrichtung
PCT/EP2008/067572 WO2009080595A2 (fr) 2007-12-21 2008-12-15 Dispositif à chambre de combustion

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EP2227629A2 EP2227629A2 (fr) 2010-09-15
EP2227629B1 true EP2227629B1 (fr) 2012-02-29

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AT (1) ATE547610T1 (fr)
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WO (1) WO2009080595A2 (fr)

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DE102010043337B4 (de) 2010-11-03 2023-01-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. Fluidzuführungsvorrichtung
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EP2881666A1 (fr) * 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Support de buse en mousse métallique
DE102018112389A1 (de) * 2018-05-23 2019-11-28 Deutsches Zentrum für Luft- und Raumfahrt e.V. Injektorvorrichtung, Brennkammersystem und Verfahren zum Einbringen von reaktionsfähigem Fluid in eine Brennkammer
DE102020124413A1 (de) 2020-09-18 2022-03-24 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammeranordnung
DE102021109484A1 (de) 2021-04-15 2022-10-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Triebwerkseinheit für einen Raketenantrieb und Brennkammervorrichtung

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WO2009080595A2 (fr) 2009-07-02
EP2227629A2 (fr) 2010-09-15
DE102007063539A1 (de) 2009-06-25
WO2009080595A3 (fr) 2010-04-01
ATE547610T1 (de) 2012-03-15

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